The 1973 formula racer ‘Loki’ was built by Ernest Prosch. A single-place, mid-wing monoplane, it raced at Reno in 1973 and 1974.
Wingspan: 17’10”
Length: 19’11”
Seats: 1
1 engine
Promavia Jet Squalus / General Avia Jet Squalus / Alberta Aerospace Phoenix FanJet
A Belgian enterprise, the Jet Squalus was designed and built around the Garrett TFE109 engine by General Avia in Italy. Designed by Stelio Frati, the prototype Jet Squalus made a successful first flight on April 30, 1987. Three prototypes of the “all through” side by side seat trainer were built and flown to Belgium. The Squalus was promoted as “the first and only third generation global trainer”, offering ab initio and advanced training from one cockpit.
Two proto¬types of the Jet Squalus are being built by General Avia in Italy, the first powered by a Garrett TFE-109 turbofan, and the second by a more powerful Williams International FJ-44. Following completion of initial flight trials the aircraft will be flown to Belgium, where production, marketing, and support of the “all-¬through” jet trainer will be administered by Promavia.
The initial 1,330 lb st (5.92 kN) -1 unit was replaced by the Garrett TFE 109-3 turbofan of 1,600 lb st (7,12 kN).
Light weapons and/or drop tanks can be carried on underwing hardpoints.
No orders had been placed for the aircraft by 1988.
In 1995 the Belgian company Promavia licensed Alberta Aerospace to begin development of an ab initio trainer version of its Jet Squalus, under the name Phoenix FanJet. Eventually Promavia sold Alberta Aerospace the flying Jet Squalus prototype for conversion (to include new Williams- Rolls FJ44 turbofan engine in a revised airframe, new “glass” cockpit, larger flying control surfaces and more), allowing certification in about the year 1999. After Promavia ceased trading, Alberta Aerospace purchased other Promavia assets, allowing eventual production in Canada.
Based in Calgary, Canada, Alberta Aerospace obtained the two prototypes built with plans to install Williams-Rolls FJ44-1a engines. Almost 80% of the structural and stress testing for certification was completed by Frati, who tested the airframe to +7 and –3.5G. With a 140 kt gear extension speed, the aircraft did not meet the 61 kt stall speed required for civilian certification for single engine, so the wing span was to be extended by four feet.
A flight demonstrator was fitted with the Williams FJ44 engine.
Jet Squalus
Engine: 1 x Garrett F109-1, 1,330 lb st (5.92 kN)
Span: 9 m
Length: 9.4 m
Wing area: 13.6 sq.m
Empty wt: 1200 kg
MTOW: 2000 kg
Max speed: 584 kph
Initial ROC: 975 m / min.
Ceiling: 11,280 m
T/O run: 366 m
Ldg run: 336 m
Fuel internal: 720 lt
Range: 1850 km
Combat radius: 460 km
Hardpoints: 4
Jet Squalus
Engine: 1 x Garrett TFE 109-3 turbofan, 1,600 lb st (7,12 kN).
Jet Squalus
Engine: 1 x Williams-Rolls FJ44-1A, 1600 lb
ROC SL: 2360 fpm
Max cruise: 315 kt at 20,000 ft
Max range; 715 nm at 261 kt
MTOW: 5100 lb
Equipped weight; 3408 lb
Useful load: 1692 lb
Fuel capacity: 185 USG
Projekt 8 Dolphin
The Danish Dolphin tandem two-seater motor glider was designed and built by the Projekt 8 I/S company of Roskilde, and 10 construction of the prototype was taking place at three separate sites near Copenhagen,
and it was expected that the first flight was to be made late in 1978.
The Dolphin is a cantilever mid-wing monoplane of mixed constrution with a T-tail, powered by a 54hp Volkswagen VW1600 engine driving a two-blade pusher propeller, mounted on a pylon and retracting rearwards behind closed doors into the top of the fuselage aft of the wings. The wings, which have 4° dihedral, have an aluminium centre section and wood and glassfibre outer panels, flaps and ailerons; there are aluminium air brakes in the upper surfaces just ahead of the flaps. The forward fuselage is a welded steel tube framework covered with a light glassfibre shell, and the rear fuselage is a wooden structure reinforced by glassfibre. The tail unit is likewise of wood, with a fixed incidence tailplane, a central trim tab in the elevator and an inset tab at the base of the rudder. There is a semiretractable rubber-sprung mainwheel plus a nosewheel and a steerable tailwheel, as well as retractable wing tip balancer wheels. The one-piece cockpit canopy opens sideways.
Span: 61 ft 5 in
Length: 27 ft 10.75 in
Height: 4 ft 3.25 in
Wing area: 223.9 sq ft
Aspect ratio: 16.8
Empty weight: 1,058 lb
Max weight: 1,653 lb
Max speed: 163 mph
Max aero-tow speed: 77.5 mph
Min sinking speed: 2.30 ft/sec at 50 mph
Best glide ratio: 32:1 at 62 mph
Progress Aero Discovery
In 1989 Progress Aero R&D Inc produced the Progress Discovery, all-composite construction two place aircraft registered N81D.
Engine: 100hp Lycoming O-235
Max speed: 200 mph
Cruise: 168 mph
Seats: 2
Progressive Aerodyne Sting Ray
The Stingray is the single seat version of the Searay.
Engine options include the Rotax 447, 503, and 582.
Engine: Rotax 447, 40 hp
HP range: 40-65
Height: 6.2 ft
Length: 21.4 ft
Wing span: 30.83 ft
Wing area: 150 sq.ft
Weight empty: 470 lb
Gross: 800 lb
Fuel cap: 6 USG
Speed max: 85 mph
Cruise: 65 mph
Range: 100 sm
Stall: 27 mph
ROC: 600 fpm
Take-off dist: 175 ft
Landing dist: 200 ft
Service ceiling: 9,000 ft
Seats: 1
Landing gear: retractable tail wheel
Progressive Aerodyne Sea Rey
A side-by-side, high wing amphibian, related to the Adventure Air Adventurer 333. It is a high wing, pusher, tail dragger configuration, and a panoramic lexan cockpit. The wings are swept back at the leading edge with a straight trailing edge to form a tapered wing. The engine is mounted on top of the wing, which is supported above the fuselage by a vertical pylon.
The Cabin is designed with side-by-side seating. Entry into the cabin is through a sliding canopy into the 44 in/112cm cockpit. Dual flight controls enable flying from either seat. There is storage space behind the seats (L48 x W44 x H17 in.) for baggage.
The SeaRey is the ability to fly unaffected with the individual dual sliding canopies either opened or closed. The retractable landing gear handles unimproved grass runways. The take off roll on land at gross weight is about 375 feet (115m). Lift off takes place at around 45-50 mph (40 – 45 knots), and 65-70 mph (55-60 knots) is the best rate of climb speed. Rate of climb is 1,000+ ft per min (300m+ per min) Solo and around 800 feet per minute (245m per min) at gross weight.
In cruise the SeaRey settles at 90 mph (80 knots). Top speed is 113 mph (98 knots). Due to the installation of special leading edge extensions on the wings, the stall is very docile and the aircraft is spin resistant. Upon throttling back and applying 20 degrees of flaps, the aircraft slows to the stall speed of around 40 mph (34 knots). The stall is gentle and straightforward and recovery is conventional. The retractable undercarriage comes with a simple manual system or alternatively an electric mechanism. An over center lock mechanism is a feature of this simple design.
Best approach speed for a water landing is 65 – 70 mph (55-60 knots) with 10 degrees of flaps. Upon reaching short final, 20 degrees of flaps can be initiated to further slow the aircraft’s touch down speed on the water. Landing flare begins lower than conventional land-only aircraft. A nice touch down speed is 45-50 mph (40-45 knots). This lands the aircraft “on step” and produces very smooth contact with the water.
The SeaRey is capable of handling quite rough water conditions but until such time as the pilot has developed their seaplane water experience, operations in moderate conditions with wave size under 12 inches (30cm), is recommended.
With 20 degrees of flaps for takeoff the SeaRey will come “on plane” in around 4 seconds. A further 6 to 8 seconds to get airborne. The hull produces a very flat spray pattern preventing water from going through the propeller. Accelerating to 45-50 mph (40-45 knots) to rotate and lift off. Established in the climb and at a safe height, reduce the flaps to 10 degrees.
The LSA Searay has dual controls with electric trim, and engine options include 65, 74, 80, and 115 hp Rotaxs.
The basic kit was $21,900 less engine in 2000.
By 2012, the American-made SeaRey has been out in kit form for 21 years (600 kits delivered) and was also an S-LSA. The 2012 models were the Sport and Elite S-LSAs, and the LSX kit (E-LSA or EAB). Prices: US$144,000 (Elite); US$125,000 (Sport) and US$34,900 (LSX airframe-only kit).
SeaRay
Engine: Rotax 912 (80hp)
Cruise Speed: 85 mph
Top Speed: 105 mph
Stall Speed: 40 mph
VNE: 120 mph
Rate of Climb: 650 fpm
Takeoff Land: 400 feet
Takeoff Water: 400 feet
Empty Weight: 820 lbs
Gross Weight: 1370 lbs
Useful Load: 550 lbs
Length: 22′ 5″
Wheel Track: 78 inches
Height: 77 inches
Fuel Capacity: 18 US gallons (optional 26 gal)
Wing Span: 30′ 10″
Endurance: 3.5 to 4 hours
Wing Area: 157 sq. feet
Cabin Width: 44 inches
Root Chord: 76 inches
Cabin Height: 38.5 inches
Tip Chord: 46 inches
Above Seat: 33.5 inches
Aspect Ratio: 6.055
Baggage Area: 13 cubic feet
Taper Ratio: 0.6
Baggage l w h: 48 x 44 x 17 in.
L.E. Sweep: 7.5 degrees
Hull Draft: 10 inches
Stab. Span: 110 inches
Flap Settings: 13, 24, 35 degrees
Engine: Rotax 912s (100hp)
Cruise Speed: 93 mph
Top Speed: 113 mph
Stall Speed: 40 mph
VNE: 120 mph
Rate of Climb: 800 fpm
Takeoff Land: 375 feet
Takeoff Water: 375 feet
Empty Weight: 830 lbs
Gross Weight: 1370 lbs
Useful Load: 540 lbs
Length: 22′ 5″
Wheel Track: 78 inches
Height: 77 inches
Fuel Capacity: 18 US gallons (optional 26 gal)
Wing Span: 30′ 10″
Endurance: 3.5 to 4 hours
Wing Area: 157 sq. feet
Cabin Width: 44 inches
Root Chord: 76 inches
Cabin Height: 38.5 inches
Tip Chord: 46 inches
Above Seat: 33.5 inches
Aspect Ratio: 6.055
Baggage Area: 13 cubic feet
Taper Ratio: 0.6
Baggage l w h: 48 x 44 x 17 in.
L.E. Sweep: 7.5 degrees
Hull Draft: 10 inches
Stab. Span: 110 inches
Flap Settings: 13, 24, 35 degrees
Engine: Rotax 914 (115hp)
Cruise Speed: 100 mph
Top Speed: 120 mph
Stall Speed: 42 mph
VNE: 120 mph
Rate of Climb: 900 fpm
Takeoff Land: 350 feet
Takeoff Water: 350 feet
Empty Weight: 850 lbs
Gross Weight: 1370 lbs
Useful Load: 520 lbs
Length: 22′ 5″
Wheel Track: 78 inches
Height: 77 inches
Fuel Capacity: 18 US gallons (optional 26 gal)
Wing Span: 30′ 10″
Endurance: 3.5 to 4 hours
Wing Area: 157 sq. feet
Cabin Width: 44 inches
Root Chord: 76 inches
Cabin Height: 38.5 inches
Tip Chord: 46 inches
Above Seat: 33.5 inches
Aspect Ratio: 6.055
Baggage Area: 13 cubic feet
Taper Ratio: 0.6
Baggage l w h: 48 x 44 x 17 in.
L.E. Sweep: 7.5 degrees
Hull Draft: 10 inches
Stab. Span: 110 inches
Flap Settings: 13, 24, 35 degrees
Pro.Mecc Sparvieo
Entirely in composite and carbon-fiber. Engine options include the Rotax 912UL 100Hp.
2009 Price: 49500 EURO. The kit price was 27.000€ (without engine and instruments).
Sparviero
Stall: 31 kt / 36 mph / 58 kmh
Cruise: 103 kt / 118 mph / 190 kmh
VNE: 130 kt / 149 mph / 240 kmh
Empty Weight: 290 kg / 639 lbs
MTOW Weight: 450 kg / 992 lbs
Take-off distance (50ft obstacle): 390 ft / 120 m
Landing distance (50ft obstacle): 490 ft / 150 m
Pro-Fe Banjo
The Banjo sailplane is of mixed construction. Its 13.3 m (43.6 ft) span wing is strut-braced with one lift strut per side and uses a plywood box spar and spruce wing ribs, with the leading edge of the wing covered in plywood and the rear portion covered in aircraft fabric covering. The nose ribs are expanded polystyrene while the ailerons are made of wood and covered in fabric. The wing airfoil is an SM701 at the wing root transitioning to a Wortmann FX-60-126 at the wing tip, while the tailplane uses a Wortmann FX-71-L-150/30 airfoil. The fuselage is of fibreglass monocoque construction, while its one-piece bubble canopy is made from polycarbonate. The aircraft has fixed monowheel landing gear with a wheel brake and upper wing surface air brakes.
Variants:
Banjo
Unpowered single-seat sailplane with a 13.3 m (43.6 ft) span wing. Four were reported completed and flying in 1998. In production in 2011.
Banjo-MH
Powered version of the Banjo, with a retractable tractor configuration Hirth F33 two stroke 21 kW (28 hp) motor powering a two-bladed wooden propeller. Fuel capacity is 14 litres (3.1 imp gal; 3.7 US gal), gross weight is 260 kg (573 lb) and load limits +4 and -2g. The aircraft has a best glide ratio of 28:1. In production in 2011.
DuoBanjo
Two seats in tandem version, with two side-by-side main wheels mounted in the fuselage and a retractable tractor configuration Rotax 447 two-stroke 30 kW (40 hp) motor powering a ProFe 1.4 m (4.6 ft) two-bladed wooden propeller. Wing span is 16 m (52.5 ft), fuel capacity is 27 litres (5.9 imp gal; 7.1 US gal), gross weight is 460 kg (1,014 lb) and load limits +4.4 and -2.4g. The aircraft has a best glide ratio of 29:1. In production in 2011.
The Banjo wing is based on the SM701 airfoil, trapezoidal outer part is modified into FX-60-126. Wingtips are equipped with winglets. Basic element of the construction is a plywood, box section beam and ribs made from spruce scantlings. Front part of the ribs is made from expanded polystyrene. Leading edge of the wing is covered by plywood and forms a torsion box. Polyester fabric covers trailing part of the wing. On the upper part of the wing are located hinged aerodynamic brakes. Wooden construction ailerons are also covered by a polyester fabric. They are operated via Dural tube rods. Wings are supported by shaped struts. Wing is fixed to the fuselage by mountings located on the wing beam and on the trailing edge section.
Fuselage, including the tail fin, is formed from a fiberglass monocoque. Monocoque is reinforced by plywood ribs. Ribs are utilized as wings, struts, undercarriage wheel and rescue system mountings.
Cockpit (closed type) is covered by a one-piece canopy made from a splinter-proof polycarbonate (Makrolon). There is a ventilation window on the side of the canopy. Control stick is a classic style type. The cockpit is equipped with aerodynamic brakes lever (left side), rope release control (“T” shaped handle on the instrument panel) and trim handle. The cockpit is ventilated via ventilation outlets, located on the instrument panel. Adjustable pilot’s seat is equipped with 4-point safety belts.
The Banj MH Cockpit has engine throttle (left side), power unit position selector, ignition switch, starter, propeller stop control and main power switch (on the right side of the cockpit).
Fixed undercarriage consists of the main unsprung wheel (outer radius 400mm) and uncontrollable tail wheel (outer radius 140mm). The main wheel is fitted with a disk brake. The brake is operated via a cycle brake lever, mounted on the control stick.
Tail surfaces are “T” shaped. Horizontal tail surfaces have similar construction as the wing and use modified Wortmann FX-71-L-150/30 airfoil.
Controls and instrumentation. The instrument panel of the plane is equipped with the following instruments: airspeed indicator, combined electronic altimeter/variometer, compass and bank indicator. The Banjo MH instrument panel also has RPM gauge, fuel gauge, and engine temperature gauge. Power unit management panel is located on the right side of the cockpit. Instrumentation can be customized according to customer’s requirements.
The DuoBanjo is equipped with one instrument panel, containing following instruments: airspeed indicator, altimeter, variometer, RPM gauge, fuel gauge, engine temperature gauge, compass and bank indicator. Power unit management panel is located on the right side of the cockpit.
System of controls. Ailerons and elevator are operated via rods, equipped with swiveling joint ends. Levers are fitted with ball bearings. Rudder is cable controlled. Aerodynamic brakes are also cable controlled, in combination with springs. The DuoBanjo is equipped with dual set of controls, however lifting/retracting of the power unit can be controlled only from the front seat. Control sticks are classic style type. Seats are equipped with 4-point safety belts.
The powered Banjo power unit is based on the engine HIRTH F33 B, equipped with an electric starter, belt reducer and two-blade propeller. Power unit can be lifted or retracted into the enclosed power unit bay during the flight.
Fuel system. Alu fuel tank is located in the fuselage and it can contain 14 liters of the fuel. It is equipped with fuel float system, measuring quantity of the fuel in the tank. Filler neck is located on the left side of the fuselage, below the wing. The DuoBanjo has 27 liters of the fuel.
Electrical system. The main source of the energy is an on-board accumulator 12V-14Ah, which is recharged by the engine. The accu feeds the lifting/retracting system of the power unit together with the electric starter.
Specifications:
Banjo
Wing span: 13,3 m
Length: 6,3 m
Wing area: 10,5 sq.m
Main undercarriage wheel diameter: 400 mm
Tail wheel diameter: 140 mm
MTOW: 220 kg
Load factor: +4,4/-2,2 G
Max. speed VNE: 140 km/h
Max. speed in turbulence VB: 110 km/h
Stall speed: 50 km/h
Min. sink: 0,68 m/s
L/D: 28
Number of seats: 1
Banjo-MH
Wing span: 13,3 m
Length: 6,3 m
Wing area: 10,5 sq.m
Main undercarriage wheel diameter: 400 mm
Tail wheel diameter: 140 mm
MTOW: 260 kg
Load factor: +4/ -2 G
Max. speed VNE: 135 km/h
Max. speed in turbulence VB: 110 km/h
Stall speed: 60 km/h
Min. sink: 0,86 m/s
L/D: 28
Climb performance with MTOW: + 2m/s
Fuel tank capacity: 14 liters
Number of seats: 1
DuoBanjo
Engine: Rotax 447 UL DCDI 1V, 29 kW (6500 rpm)
Propeller: ProFe 1400mm
Wing span: 16 m
Length: 7,35 m
Height (propeller in retracted position): 1,57 m
Wing area: 13,86 sq.m
Aspect ratio: 18,3
Wing load at 460kg: 33 kg/sq.m
Number of seats: 2
Empty weight: 250 kg
MTOW: 460 kg
Max. weight of the crew: 200 kg
Min. pilot’s weight: 70 kg
Stall speed: 64 km/h
Maneuver speed Va: 130 km/h
Max. speed in turbulence Vb: 130 km/h
Max. speed Vne: 175 km/h
Min. sink (at 90 km/h): 0,9 m/s
Best L/D (at 100 km/h): 29
Cruise speed (5000 rpm): 110 km/h
Max. climb: 3 m/s
Load factor: + 4.4 / – 2.4 G
Fuel consumption, cruise: 9.5 l/h
Fuel tank capacity: 26 liters
Produits Aviatech Super Cyclone
Cruise: 165 mph
Stall: 38 mph
Range: 1150 sm
Rate of climb: 1600 fpm
Takeoff dist: 225 ft
Landing dist: 600 ft
Engine: Continental, 300 hp
HP range: 230-350
Fuel capacity: 72 USG
Empty weight: 1750 lb
Gross weight: 3500 lb
Length: 26 ft
Wing span: 39 ft
Wing area: 207 sq.ft
Cockpit width: 38 in
Landing gear: nose or tail
Proctor Kittiwake I / Mitchell-Proctor Kittiwake I
Originally designed in 1964-65 by R. G. Proctor and C. G. B. Mitchell as a dedicated single-seat glider tug aircraft. Mitchell-Procter Aircraft was set up to produce the Kittwake prototype. It was a development of the Mitchell-Prizeman Scamp design study of 1964. ‘Kit’ Mitchell was the Kittiwake’s designer, with Roy Procter in charge of building it. It had excellent visibility, sturdy landing gear.
The Kittiwake was of all-metal stressed skin construction with tricycle landing gear. The nose-wheel was steerable for taxiing and the aircraft was fitted with hydraulic brakes.
The aircraft would be capable of aerobatics with a rate of Roll 200 degrees at 103 mph (90 kn; 166 km/h). The Kittiwake had a rate of climb of 700 feet (213 metres) per minute with a 1,000 lb (454 kg) glider in tow.
The single-seat Kittiwake I is an all-metal aircraft, with low cantilever wings of parallel chord built around a single spar carrying 5° of dihedral. NACA single slotted flaps occupy the whole of the trailing edge inboard of the ailerons. The wings attach to a centre section which is integral with the fuselage, a feature intended to help construction in a small space like a garage. The straight tapered fin carries a horn balanced rudder and the constant chord tailplane has a starboard side trim tab.
The Kittiwake’s fuselage is built around four longerons, with flat sides and bottom and single curvature decking. Its overwing cockpit has a rearward sliding canopy and its fixed tricycle undercarriage has cantilever angled steel spring main legs attached to the lower longerons, giving a track of 5 ft 9 in (1.75 m). The Kittiwake I was powered by a 100 hp (75 kW) Continental O-200 engine.
The wing had generous flaps with high operating speeds which allowed for a fast descent. It had a self-starter system, provision for a radio. The Kittiwake also had a mechanism for retracting the tow rope during the descent. This design was fully aerobatic and additional fuel tanks could be fitted to extend the range.
By the middle of 1965 production tooling were being made for the wing ribs as well as spars machined.
The Kittiwake single-seat, low-wing monoplane was designed to make full use of all-metal materials and modern construction while retaining a simplicity of design that lends itself to homebuilding.
The prototype was started at Camberley but completed by BEA Engineering in 1966-7, powered by a Continental O-200-A. First flown at Lasham on 23 May 1967, it was registered G-ATXN PFA.1306. It was re-engined with a fan-cooled Lycoming O-290 at Lasham in 1972. The prototype was later known as the Mitchell-Procter Kittiwake I. Around a year and a half later the partnership was dissolved and plans for home builders were produced by Procter Aircraft Associates.
A second was built at RNAS Lee-on-Solent as an apprentice project under Lieutenant Commander Cudmore, started in 1969. First flying on 21 October 1971 sn serial XW784, at Lee-on-Solent, powered by a Rolls-Royce/Continental O-200-A.
It was subsequently registered G-BBRN. Built, one by Royal Navy apprentices in 1971 for glider towing, a larger diameter (6 ft 4 in, 1.93 m) propeller is fitted, increasing the rate of climb by 24%. A tow release hook is fitted under the tail. Only one Kittiwake II, the prototype, was built.
In later years the prototype was re-engined with a Lycoming O-290-D2 engine.
Mitchell continued development and produced the Mitchell Kittiwake II two-seater. Plans were available for both single-seat and two-seat versions, but only four were constructed. Examples built of the Kittiwake I: G-AXTN, G-BBRN (marked as XW784).
One Kittiwake was active until at least at 2005 and the other is still active. They remain on the UK Civil Register. These are the prototype, G-ATXN and the ex-Naval G-BBRN. The latter is painted, as in its Naval days, as XW784.
Kittiwake I
Engine: 1 × Rolls Royce-Continental O-200-A, 100 hp (75 kW)
Propeller: 2-bladed McCauley 69CM52, 5 ft 9 in (1.75 m) diameter metal, fixed pitch
Wing span: 24 ft 0 in (7.32 m)
Wing area: 105 sq ft (9.8 m2)
Length: 19 ft 7 in (5.97 m)
Height: 7 ft 6 in (2.29 m)
Empty weight: 910 lb (413 kg)
Gross weight: 1,250 lb (567 kg) for aerobatic flight
Maximum take-off weight: 1,350 lb (612 kg)
Fuel capacity 26 USG
Maximum speed: 131 mph (211 km/h; 114 kn)
Cruise speed: 122 mph (106 kn; 196 km/h) at 75% power
Stall 48 mph
Range: 540 miles (469 nmi; 869 km) at 92 mph (148 km/h)
Ferry Range with additional tanks: 600 miles (521 nm; 966 km)
Rate of climb: 850 ft/min (4.3 m/s)
Crew: 1
All Aero 